Airflow Simulator: Panel Methods in Rust

This project implements panel methods for simulating 2D potential flow around airfoils, written in Rust. Panel methods are a popular numerical technique in aerodynamics, offering a way to compute flow fields, lift, and other aerodynamic properties for streamlined bodies.

Having primarily worked with Rust to build CLI and system-level tools, mainly for embedded devices; this project allows me to expand into scientific and graphical applications using Rust. The purpose of this project is to experiment with a relatively complex task that blends mathematics, aerodynamics, and programming.

Status: This is a Work in Progress (WIP).

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Features

Completed

• Airfoil Generation:

  • Generates 2D airfoil shapes from NACA 4-digit series (e.g., NACA 0012).
  • Uses mean camber line and thickness distribution equations to build airfoil surfaces.

• Panel Definition:

  • Divides airfoil geometry into panels with control points and normal vectors.

• Panel Method Solver:

  • Implements a source-panel method for potential flow.
  • Solves a linear system of equations to compute panel strengths.
  • Includes freestream influence and angle of attack.

• Pressure Distribution:

  • Calculates pressure coefficients ($C_p$) along the airfoil surface.
  • Differentiates between upper and lower surfaces.

• Performance Metrics:

  • Computes aerodynamic coefficients:
    • Lift Coefficient ($C_L$)
    • Drag Coefficient ($C_D$) (from panel solutions, viscous effects not included)
    • Moment Coefficient ($C_M$) (about the quarter-chord).

• Streamline Visualization:

  • Calculates streamlines starting from specified points in the flow field.
  • Displays velocity variations along streamlines.
  • 4th order Runge-Kutta (RK4) numerical integration for solving streamlines and velocity fields.

• Velocity Field Visualization:

  • Generates a velocity field using a user-defined grid density.
  • Displays vectors scaled by velocity magnitude.

• Graphical Interface:

  • Built with eframe/egui for an interactive UI.
  • Includes adjustable sliders for parameters like:
    • Angle of attack.
    • Freestream velocity.
    • Grid density for velocity fields.
  • Interactive plots using egui_plot.

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Planned Adjustments and Features

1. Improved Solver:

   • Extend panel method to include vortex panels for handling lifting flows more accurately.
   • Account for leading-edge and trailing-edge flow features.

2. Boundary Conditions:

   • Improve influence coefficient calculations for higher precision.

3. Viscous Effects:

   • Implement an approximation for boundary layer and drag due to viscosity.

4. 3D Extension:

   • Experiment with lifting-line theory or a 3D panel method for finite wings.

5. Interactive Airfoil Design:

   • Allow users to define custom airfoil shapes or load geometry from files.

6. Performance Visualization:

   • Add visual comparisons of lift and drag for different airfoils and flow conditions.

7. Optimized Numerical Methods:

   • Use parallel computing for large grids or higher panel resolutions.

8. Validation:

   • Compare results with CFD software or analytical solutions for benchmark cases.

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How to Run

1. Clone the repository:

   git clone https://github.com/boulama/flowvisualizer.rs
   cd flowvisualizer.rs

2. Build and run the application:

   cargo run --release

3. Use the interactive GUI to:

   • Input a NACA code (e.g., 0012) to generate an airfoil.
   • Adjust flow conditions, such as angle of attack and velocity.
   • Visualize results like streamlines, pressure distribution, and velocity fields.

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Dependencies

• eframe and egui: For GUI and plotting.
• nalgebra: For vector and matrix operations.
• egui_plot: For creating interactive plots.
• std::f64::consts: For constants like $\pi$.

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Screenshots

Contributing

This project is open for contributions! If you have ideas for enhancements or want to tackle a specific feature, feel free to fork the repository and submit a pull request.

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Acknowledgments

• NACA equations
• VI. The Panel Method: An Introduction
• Inspiration for panel methods from classic the classic Fundamentals of Aerodynamics by John D. Anderson.

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License

This project is licensed under GLWTPL. See LICENSE for details.